CN107097980A - A kind of non-firer's stage separation structure - Google Patents
A kind of non-firer's stage separation structure Download PDFInfo
- Publication number
- CN107097980A CN107097980A CN201710202546.9A CN201710202546A CN107097980A CN 107097980 A CN107097980 A CN 107097980A CN 201710202546 A CN201710202546 A CN 201710202546A CN 107097980 A CN107097980 A CN 107097980A
- Authority
- CN
- China
- Prior art keywords
- shape memory
- connection piece
- memory alloy
- bay section
- firer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
- Non-Disconnectible Joints And Screw-Threaded Joints (AREA)
Abstract
The invention discloses a kind of non-firer's stage separation structure, including shape memory alloy connection piece, heating plate and collector, shape memory alloy connection piece is less than one end bending deformation in the case of phase transition temperature, the other end passes through the bay section of aircraft first and the second bay section, two bay sections are fixedly connected by locking member, collector is covered on locking member, for domestic initiation, meet the connection separation demand of spacecraft, it is applied in spacecraft small size separator, pass through memorial alloy, heating plate is realized with the connection between bay section with separating, this is simple in construction, it is reusable, install simple.
Description
Technical field
The present invention relates to a kind of non-firer's stage separation structure, belong to the docking of aircraft two-stage and separation field.
Background technology
The connection of spacecraft and isolation technics are the important research contents of space industry.Existing piece-rate system is mainly bag
Several typical combinations such as band, spring, blasting bolt, retro-rocket, but comparatively, traditional approach isolating construction space
And shock loading is relatively large, separator architecture quality is big.With the development of space technology, in the urgent need to develop small volume,
The even shock-free new non-firer's connection separator of light weight, low impact, is needed with adapting to growing AEROSPACE APPLICATION
Ask.
At present, the application of domestic firer's isolation technics is still quite varied, the stage separation of guided missile and carrier rocket, head body
Priming system is all largely employed in separation and satellite and the rocket separation.The external especially advanced American-European countries of space technology has carried out
Separator research based on non-priming system, the external power source using marmem as non-priming system separator is carried out
Separator is designed, and is amplified being used as power for marmem by complex mechanism, and intermediate transfer link is complicated, manufacture
Big with assembly difficulty, disengaging time is longer.The domestic research to non-priming system is in the junior stage, and correlation technique is temporarily real without application
Example.
The content of the invention
The technology of the present invention solves problem：To overcome the deficiencies in the prior art there is provided a kind of non-firer's stage separation structure,
The need for adapting to the non-firer of the similar aircraft of China and small size separator.
The technical solution of the present invention：
A kind of non-firer's stage separation structure, including shape memory alloy connection piece, heating plate and collector, shape memory
Alloy connector is less than one end bending deformation in the case of phase transition temperature, and the other end passes through the bay section of aircraft first and the second bay section,
Two bay sections are fixedly connected by locking member, collector is covered on locking member, heating plate is connected on the first bay section side wall, shape
At the bending deformation of shape memory alloys connector when being close to separate between heating plate, bay section, heating plate produces heat, and by heat transfer
To shape memory alloy connection piece, more than being straightened in the case of 60 DEG C~120 DEG C of austenite transition temperature at bending deformation, to flight
Connection between the bay section of device first and the second bay section loses constraint, and the first bay section and the second bay section are started in aerodynamic force or solid
Separation is realized in the presence of machine jet pressures.
Shape memory alloy connection piece material is Ti-Ni alloy, and titanium alloy ratio is 49%~51%, and nickel alloy ratio is
49%~51%.
Shape memory alloy connection piece material is titanium titanium monel, and titanium alloy ratio is 48%~51%, nickel alloy ratio
Example is 48%~51%, and copper alloy ratio is 0.1~2%.
Shape memory alloy connection piece material martensitic transformation temperature scope is -10 DEG C~30 DEG C.
Gap coordinates between shape memory alloy connection piece and two bay sections, and fit clearance is 0.1~1mm.
When being separated between bay section, electric power system is powered to the heating plate of shape memory alloy connection piece or by solid on bullet
Flame during body engine ignition is heated or first leads to certain electricity to heating plate, then is heated by flame, makes to add
Backing produces heat.
The treatment temperature of shape memory alloy connection piece bending deformation is 400 DEG C~500 DEG C, and processing time is 0.5~2h.
The present invention has the advantages that compared with prior art：
The present invention proposes a kind of non-firer's stage separation structure, is domestic initiation, effectively solves to connect between the level of aircraft
With separation problem, it is applied, is realized by memorial alloy, heating plate between bay section in spacecraft small size separator
Connection with separating, this is simple in construction, reusable, connection reliable, separation is rapid, lock firm, lightweight, small volume,
Install simple.
Brief description of the drawings
Fig. 1 is application schematic diagram of the present invention；
Fig. 2 is that bay section of the present invention separates pre-structure figure；
Fig. 3 is structure chart after bay section of the present invention separation.
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in Figure 1 and Figure 2, a kind of non-firer's stage separation structure, including shape memory alloy connection piece 1, heating plate 2
With collector 3, the material of shape memory alloy connection piece 1 is Ti-Ni alloy or titanium monel, works as shape memory alloy connection piece
When material elects Ti-Ni alloy as, titanium alloy ratio is 49%~51%, and nickel alloy ratio is 49%~51%, when shape memory is closed
When golden connector material is titanium titanium monel, titanium alloy ratio is 48%~51%, and nickel alloy ratio is 48%~10%, copper
Alloy ratio is 0.1~2%.
The material martensitic transformation temperature scope of shape memory alloy connection piece 1 is -10 DEG C~30 DEG C, and marmem connects
Fitting 1 is less than one end bending deformation in the case of phase transition temperature, and the other end passes through the bay section of aircraft first and the second bay section, passes through lock
Two bay sections are fixedly connected by tight part, and gap coordinates between shape memory alloy connection piece and two bay sections, and fit clearance is 0.1
~1mm.Collector 3 is covered on locking member, and heating plate 2 is connected on the first bay section side wall, and shape memory alloy connection piece 1 is bent
When being close to separate between heating plate 2, bay section at deformation, electric power system is led to the heating plate of shape memory alloy connection piece on bullet
Electricity or flame when being lighted by solid engines are heated or first heating plate are led to certain electricity, then are carried out by flame
Heating, produces instantaneous high-temperature, heating plate 2 is produced heat, and transfers heat to shape memory alloy connection piece 1, and bending becomes
Exceed at shape and straighten in the case of 60 DEG C~120 DEG C of austenite transition temperature, external force is acted in the first bay section, is realized between two bay sections
Separation.
Shape memory alloy connection piece 1 is flat, before two-stage docking connection fastening, by connector 400 DEG C~500
Afterbody is shaped to the shape that is open after being cooled down at a temperature of DEG C, after aircraft two-stage docking is carried out, pacified at the plane at bay section I
Heating plate 2 is filled, heating plate 2 can be connected by circuit with control system on bullet.Pass through the accessory such as standard component and the collector of correlation
System is fastenedly connected between carrying out bullet higher level.
The specific work process of mechanism is as follows：Guided missile is sent after stage separation instruction, and control system is carried out to heating plate
Power supply, heating plate is brought rapidly up passing to shape memory alloy connection piece, when the temperature of shape memory alloy connection piece exceedes Austria
Family name's body phase becomes finishing temperature, and shape memory alloy connection piece is can occur memory and be deformed between flat, two-stage to lose connection
Part is fettered, as shown in figure 3, two-stage is initially separated in the presence of aerodynamic force and corresponding stage separation power, until between two-stage
It is kept completely separate, completes the mission of isolating construction.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (7)
1. a kind of non-firer's stage separation structure, it is characterised in that including shape memory alloy connection piece (1), heating plate (2) and
Collector (3), shape memory alloy connection piece (1) is less than one end bending deformation in the case of phase transition temperature, and the other end passes through flight
Two bay sections, are fixedly connected by the bay section of device first and the second bay section by locking member, and collector (3) is covered on locking member, heating
Piece (2) is connected on the first bay section side wall, is close at shape memory alloy connection piece (1) bending deformation between heating plate (2), bay section
During separation, heating plate (2) produces heat, and transfers heat at shape memory alloy connection piece (1), bending deformation more than Austria
Straightened in the case of 60 DEG C~120 DEG C of family name's body phase temperature, the connection between the bay section of aircraft first and the second bay section is lost about
Beam, the first bay section and the second bay section realize separation in the presence of aerodynamic force or solid engines jet pressures.
2. a kind of non-firer's stage separation structure as claimed in claim 1, it is characterised in that shape memory alloy connection piece
(1) material is Ti-Ni alloy, and titanium alloy ratio is 49%~51%, and nickel alloy ratio is 49%~51%.
3. a kind of non-firer's stage separation structure as claimed in claim 1, it is characterised in that shape memory alloy connection piece
(1) material is titanium titanium monel, and titanium alloy ratio is 48%~51%, and nickel alloy ratio is 48%~51%, copper alloy ratio
Example is 0.1%~2%.
4. a kind of non-firer's stage separation structure as claimed in claim 2 or claim 3, it is characterised in that marmem is connected
Part (1) material martensitic transformation temperature scope is -10 DEG C~30 DEG C.
5. a kind of non-firer's stage separation structure as claimed in claim 1, it is characterised in that shape memory alloy connection piece with
Gap coordinates between two bay sections, and fit clearance is 0.1~1mm.
6. a kind of non-firer's stage separation structure as claimed in claim 1, it is characterised in that when being separated between bay section, on bullet
Flame when electric power system is powered or lighted by solid engines to the heating plate at shape memory alloy connection piece is added
Heat first leads to certain electricity to heating plate, then is heated by flame, heating plate (2) is produced heat.
7. a kind of non-firer's stage separation structure as claimed in claim 1, it is characterised in that shape memory alloy connection piece
(1) treatment temperature of bending deformation is 400 DEG C~500 DEG C, and processing time is 0.5~2h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710202546.9A CN107097980B (en) | 2017-03-30 | 2017-03-30 | A kind of non-firer's stage separation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710202546.9A CN107097980B (en) | 2017-03-30 | 2017-03-30 | A kind of non-firer's stage separation structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107097980A true CN107097980A (en) | 2017-08-29 |
| CN107097980B CN107097980B (en) | 2019-07-12 |
Family
ID=59674745
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710202546.9A Active CN107097980B (en) | 2017-03-30 | 2017-03-30 | A kind of non-firer's stage separation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107097980B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439884A (en) * | 2018-05-02 | 2019-11-12 | 长春理工大学 | A kind of repeatable locking axial locking structure using memorial alloy |
| CN113460319A (en) * | 2020-03-31 | 2021-10-01 | 海鹰航空通用装备有限责任公司 | Tandem booster fireless separation structure and aircraft with same |
| CN113650809A (en) * | 2018-08-13 | 2021-11-16 | 蓝箭航天空间科技股份有限公司 | Spacecraft cabin segment blanking cover, cabin segment structure and spacecraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100111822A (en) * | 2009-04-08 | 2010-10-18 | 한국항공대학교산학협력단 | Separation device for the spacecraft's appurtenances |
| EP2450280B1 (en) * | 2010-11-05 | 2012-12-26 | Honeywell International Inc. | Payload launch lock mechanism |
| CN102910299A (en) * | 2008-09-03 | 2013-02-06 | 北京航空航天大学 | Connecting and unlocking mechanism driven by SMA (Shape Memory Alloy) wire |
| CN105253332A (en) * | 2015-10-30 | 2016-01-20 | 北京卫星制造厂 | Large-bearing low-impact connecting and separating device based on memory alloy driving |
| CN105711860A (en) * | 2016-02-05 | 2016-06-29 | 大连理工大学 | Improved non-fire-work dot-type separation device |
-
2017
- 2017-03-30 CN CN201710202546.9A patent/CN107097980B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102910299A (en) * | 2008-09-03 | 2013-02-06 | 北京航空航天大学 | Connecting and unlocking mechanism driven by SMA (Shape Memory Alloy) wire |
| KR20100111822A (en) * | 2009-04-08 | 2010-10-18 | 한국항공대학교산학협력단 | Separation device for the spacecraft's appurtenances |
| EP2450280B1 (en) * | 2010-11-05 | 2012-12-26 | Honeywell International Inc. | Payload launch lock mechanism |
| CN105253332A (en) * | 2015-10-30 | 2016-01-20 | 北京卫星制造厂 | Large-bearing low-impact connecting and separating device based on memory alloy driving |
| CN105711860A (en) * | 2016-02-05 | 2016-06-29 | 大连理工大学 | Improved non-fire-work dot-type separation device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439884A (en) * | 2018-05-02 | 2019-11-12 | 长春理工大学 | A kind of repeatable locking axial locking structure using memorial alloy |
| CN113650809A (en) * | 2018-08-13 | 2021-11-16 | 蓝箭航天空间科技股份有限公司 | Spacecraft cabin segment blanking cover, cabin segment structure and spacecraft |
| CN113460319A (en) * | 2020-03-31 | 2021-10-01 | 海鹰航空通用装备有限责任公司 | Tandem booster fireless separation structure and aircraft with same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107097980B (en) | 2019-07-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107097980B (en) | A kind of non-firer's stage separation structure | |
| US20090189014A1 (en) | Attachment of a multiflow turbojet engine to an aircraft | |
| CN103253384B (en) | Low impact unlocking device based on shape memory alloy spring, and application method thereof | |
| CN105066796B (en) | A kind of guided missile hanging separating mechanism | |
| EP3408506B1 (en) | Combined cycle power plant | |
| US20140047849A1 (en) | Spherical button washer for exhaust duct liner hanger | |
| CN110239746A (en) | A kind of hexagon microsatellite separation tripper | |
| WO2014055717A4 (en) | Aero boost - gas turbine energy supplementing systems and efficient inlet cooling and heating, and methods of making and using the same | |
| CN102155885A (en) | Cruise target projectile | |
| CN109352582A (en) | A kind of aero-engine calotte assembling jig and application method | |
| US20140048166A1 (en) | Pivoting ball stop for exhaust duct liner hanger | |
| US7217331B2 (en) | Method for shaping structures comprised of aluminum alloys | |
| CN104226722A (en) | Machining method of TB3 bar for aerospace electric explosion valve | |
| CN106777613A (en) | A kind of light titanium alloy rapid shaping carrier rocket of optimization bundlees the preparation method of bearing | |
| US20160290230A1 (en) | Heat pipe cooling system for a turbomachine | |
| CN102400718A (en) | NiTi shape memory alloy blade for deformable turbofan engine | |
| CA2325126C (en) | Method and system for feeding a cool air inlet of the cabin of an aircraft propelled by at least one jet engine | |
| CN109625327A (en) | Hot melt suitable for vacuum environment, which breaks, solves lock release | |
| CN109234650A (en) | Single-piece expanded type laminar flow inlet lip covering | |
| McDaniel et al. | A combined cycle power conversion system for small modular LMFBRs | |
| CN105874088A (en) | Method and system | |
| EP3495631A1 (en) | Fairings for power generation machines | |
| CN110159456A (en) | Thrust chamber | |
| CN204881357U (en) | Separating mechanism is hung to guided missile | |
| Lawrence | Nuclear thermal rocket propulsion systems |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |